EP1461248A1 - Vehicule spatial a radiateurs deployables - Google Patents
Vehicule spatial a radiateurs deployablesInfo
- Publication number
- EP1461248A1 EP1461248A1 EP02799822A EP02799822A EP1461248A1 EP 1461248 A1 EP1461248 A1 EP 1461248A1 EP 02799822 A EP02799822 A EP 02799822A EP 02799822 A EP02799822 A EP 02799822A EP 1461248 A1 EP1461248 A1 EP 1461248A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- antenna
- face
- radiator
- axis
- main
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 239000011435 rock Substances 0.000 claims description 2
- 239000007789 gas Substances 0.000 description 2
- 239000003380 propellant Substances 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 230000000593 degrading effect Effects 0.000 description 1
- 210000003746 feather Anatomy 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 230000000873 masking effect Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
- B64G1/2221—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state characterised by the manner of deployment
- B64G1/2222—Folding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
- B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control
- B64G1/503—Radiator panels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
Definitions
- It relates more particularly to space vehicles intended to constitute satellites placed in a geosynchronous orbit, and in particular in a geostationary orbit, stabilized so that a determined axis of the satellite remains directed towards the earth.
- the main telecommunication antennas 14 are mounted laterally on either side of the satellite, at a distance from the east and west faces (or from one of them only) in order to clear their transmission or reception lobe. These antennas main must remain precisely pointed towards the areas of the earth to be covered, because they have a narrow lobe.
- fixed radiative surfaces 24 are provided on the north and south faces of the satellite and are thermally connected to the loads of the satellite which generate heat, for example by heat pipes.
- the increase in thermal power generated on recent high-power satellites makes the heat dissipation surface of fixed radiative surfaces insufficient. Consequently, satellites have been designed which also have deployable radiators, which are applied against the body of the satellite during launch and which are subsequently deployed, generally by tilting, to bring them in a north and / or south orientation). In particular, attempts have been made to produce configurations such that the radiators, in the deployed state, are not placed in the lobe of the main telecommunication antennas.
- the present invention aims in particular to provide a spacecraft having an arrangement of deployable radiators avoiding at the same time masking the field of vision of the antenna or main telecommunication antennas, of interfering with the jet of the generator nozzles and of obstruct the field of vision of an omnidirectional antenna carried by the rear face of the spacecraft.
- the invention notably proposes a spacecraft having a body, at least one main telecommunication antenna having a determined orientation relative to the body, at least one omnidirectional antenna having a field of vision opposite that of the antennas main and at least one radiator deployable by tilting around a tilting axis linked to the body of the vehicle between a storage position where it is applied against the body and a deployed position, characterized in that said tilting axis is placed substantially in the plane of a face of the body which is parallel to the orientation of the axis of the field of vision of the omnidirectional antenna and to the faces (or to the face) carrying the main antenna, said tilting axis being placed so that the radiator can tilt at an angle close to 180 ° from a storage position where it is pressed against a face carrying a solar panel to a position where it extends end substantially in the plane of the face which brings it to the stored state.
- the spacecraft is a satellite having a body, at least one main telecommunication antenna carried by an east or west face, at least one omnidirectional antenna carried by a face opposite the earth and at least one radiator deployable by tilting around an axis linked to the body of the satellite between a storage position where it is applied against the north or south face of the body and a deployed position, characterized in that the said axis is placed substantially in the plane of the north or south face against which the stored radiator is applied and is placed so that the radiator rocks at an angle equal to or close to 180 ° from the storage position to a position where it extends east and west from the body, behind a main antenna.
- the pivoting axes of the radiators are parallel to the direction Z, the maximum length of the radiators making it possible to store them (except in the case of a radiator er! IêT ⁇ x ⁇ àr iê ⁇ Iiâbles-r ⁇ ne sur rautre) " " esMimITEe ⁇ àia width-du satellite in the X direction (east-west direction), width which is generally less than the length in the Z direction.
- the tilt axes substantially at 45 ° from the Z direction, it is possible to give the radiators an almost equal to the length of the satellite in the Z direction, provided that the deployment of the radiators for certain orientations of the solar panels is not controlled.
- FIG. 6 is a partial perspective view of the mounting of a radiator according to FIG. 5.
- the satellite the basic architecture of which is shown in FIG. 2, where the elements corresponding to those of FIG. 1 have the same reference number, carries, in addition to the fixed radiative surfaces 24 of conventional constitution, four radiators 25. Two of these radiators are provided for tilting symmetrically about an axis 30 of direction Z, from a storage position where they are pressed against the north face to a deployed position where they are practically in the extension of this north face, behind the reflectors of the main antennas 14 so as not to interfere with the lobe of these antennas.
- the width W of these radiators is thus limited to that of the free location behind the antenna reflectors 14.
- the radiators deployed do not interfere with the lobe of the main antennas. They are also not placed in the jet of the nozzles 16 and the thrust generators 16 intended to operate when the satellite is already in its final orbit, while the radiators are deployed. Finally, as shown in FIG. 4, they also do not penetrate into the lobe ⁇ of the omnidirectional antennas 26, even for a solid angle which can slightly exceed 2 ⁇ steradians.
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Environmental & Geological Engineering (AREA)
- Life Sciences & Earth Sciences (AREA)
- Biodiversity & Conservation Biology (AREA)
- Health & Medical Sciences (AREA)
- Environmental Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Toxicology (AREA)
- Details Of Aerials (AREA)
- Aerials With Secondary Devices (AREA)
- Photovoltaic Devices (AREA)
- Variable-Direction Aerials And Aerial Arrays (AREA)
Abstract
Description
Claims
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0200006 | 2002-01-02 | ||
FR0200006A FR2834274B1 (fr) | 2002-01-02 | 2002-01-02 | Vehicule spatial a radiateurs deployables |
PCT/FR2002/004428 WO2003059740A1 (fr) | 2002-01-02 | 2002-12-18 | Vehicule spatial a radiateurs deployables |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1461248A1 true EP1461248A1 (fr) | 2004-09-29 |
EP1461248B1 EP1461248B1 (fr) | 2006-06-21 |
Family
ID=8871135
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP02799822A Expired - Fee Related EP1461248B1 (fr) | 2002-01-02 | 2002-12-18 | Vehicule spatial a radiateurs deployables |
Country Status (8)
Country | Link |
---|---|
US (1) | US7036772B2 (fr) |
EP (1) | EP1461248B1 (fr) |
JP (1) | JP4317456B2 (fr) |
CN (1) | CN1321860C (fr) |
AU (1) | AU2002364459A1 (fr) |
DE (1) | DE60212709T2 (fr) |
FR (1) | FR2834274B1 (fr) |
WO (1) | WO2003059740A1 (fr) |
Families Citing this family (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7602349B2 (en) * | 2006-02-24 | 2009-10-13 | Lockheed Martin Corporation | System of stowing and deploying multiple phased arrays or combinations of arrays and reflectors |
US7874520B2 (en) * | 2006-03-21 | 2011-01-25 | Lockheed Martin Corporation | Satellite with deployable, articulatable thermal radiators |
US8714492B2 (en) | 2012-02-07 | 2014-05-06 | Lockheed Martin Corporation | Non-interfering deployable radiator arrangement for geo spacecraft |
US8960608B2 (en) | 2012-02-07 | 2015-02-24 | Lockheed Martin Corporation | Deployable radiator having an increased view factor |
CN102700728B (zh) * | 2012-06-18 | 2014-08-13 | 上海卫星工程研究所 | 一种卫星太阳电池阵在轨被遮挡的确定方法及其应用 |
FR2996526B1 (fr) | 2012-10-05 | 2015-05-15 | Thales Sa | Satellite a modules de charge utile deployables |
FR3006298B1 (fr) * | 2013-06-03 | 2016-10-14 | Astrium Sas | Vehicule spatial comprenant au moins un couple de bras porteurs muni d'un module creux de montage et procede pour la mise en oeuvre d'un tel vehicule |
US9352856B1 (en) * | 2013-12-04 | 2016-05-31 | Space Systems/Loral, Llc | Axially grooved crossing heat pipes |
US9878808B2 (en) * | 2015-01-08 | 2018-01-30 | The Boeing Company | Spacecraft and spacecraft radiator panels with composite face-sheets |
FR3031969B1 (fr) * | 2015-01-27 | 2017-01-27 | Airbus Defence & Space Sas | Satellite artificiel et procede de remplissage d'un reservoir de gaz propulsif dudit satellite artificiel |
US10118717B2 (en) * | 2015-06-02 | 2018-11-06 | Airbus Defence And Space Sas | Artificial Satellite |
US10018426B2 (en) | 2016-05-12 | 2018-07-10 | The Boeing Company | Composite heat pipes and sandwich panels, radiator panels, and spacecraft with composite heat pipes |
CN106347714B (zh) * | 2016-08-31 | 2018-06-12 | 北京空间飞行器总体设计部 | 一种具备在轨弹抛功能的舱外辐射器防护罩系统 |
CN110015444A (zh) * | 2019-03-29 | 2019-07-16 | 上海卫星工程研究所 | 中高轨道零倾角合成孔径雷达卫星构型 |
CN114408224B (zh) * | 2021-12-20 | 2024-05-17 | 中国航天科工集团八五一一研究所 | 一种空间可回收式折叠机构 |
US12017806B2 (en) * | 2022-01-21 | 2024-06-25 | Maxar Space Llc | Satellite with modular radiator panels |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5833175A (en) * | 1995-12-22 | 1998-11-10 | Hughes Electronics Corporation | Spacecraft with large east-west dimensions |
US5927654A (en) * | 1997-05-16 | 1999-07-27 | Lockheed Martin Corp. | Spacecraft with active antenna array protected against temperature extremes |
US6378809B1 (en) | 1997-10-10 | 2002-04-30 | Space Systems | AFT deployable thermal radiators for spacecraft |
US6311931B1 (en) * | 1999-12-17 | 2001-11-06 | The Boeing Company | Bi-directional momentum bias spacecraft attitude control |
US6854510B2 (en) * | 2001-04-24 | 2005-02-15 | Space Systems/Loral, Inc. | Spacecraft radiator system and method using cross-coupled deployable thermal radiators |
-
2002
- 2002-01-02 FR FR0200006A patent/FR2834274B1/fr not_active Expired - Lifetime
- 2002-12-18 WO PCT/FR2002/004428 patent/WO2003059740A1/fr active IP Right Grant
- 2002-12-18 JP JP2003559862A patent/JP4317456B2/ja not_active Expired - Lifetime
- 2002-12-18 EP EP02799822A patent/EP1461248B1/fr not_active Expired - Fee Related
- 2002-12-18 DE DE60212709T patent/DE60212709T2/de not_active Expired - Lifetime
- 2002-12-18 AU AU2002364459A patent/AU2002364459A1/en not_active Abandoned
- 2002-12-18 CN CNB028266021A patent/CN1321860C/zh not_active Expired - Fee Related
-
2004
- 2004-06-18 US US10/871,934 patent/US7036772B2/en not_active Expired - Lifetime
Non-Patent Citations (1)
Title |
---|
See references of WO03059740A1 * |
Also Published As
Publication number | Publication date |
---|---|
WO2003059740A1 (fr) | 2003-07-24 |
JP4317456B2 (ja) | 2009-08-19 |
DE60212709T2 (de) | 2007-02-22 |
FR2834274B1 (fr) | 2004-04-02 |
CN1321860C (zh) | 2007-06-20 |
FR2834274A1 (fr) | 2003-07-04 |
EP1461248B1 (fr) | 2006-06-21 |
US20050023415A1 (en) | 2005-02-03 |
AU2002364459A1 (en) | 2003-07-30 |
CN1610628A (zh) | 2005-04-27 |
US7036772B2 (en) | 2006-05-02 |
JP2005514270A (ja) | 2005-05-19 |
DE60212709D1 (de) | 2006-08-03 |
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